Waterless electrically operated propellant

ABSTRACT

An electrically operated propellant includes an electrolyte source. The electrolyte source is an ionic liquid, a polyelectrolyte, or a combination thereof. The electrically operated propellant also includes a polymeric binder. The electrically operated propellant is substantially waterless with a water content of less than 10 wt. % water based on total weight of the electrically operated propellant.

BACKGROUND

Missiles and rockets burn propellants within combustion chambers togenerate pressurized gases. The pressurized gases are directed through anozzle to provide thrust and accordingly propel the body of the missileor rocket.

Solid rocket propellants are formed with a solid oxidizer, for instanceammonium perchlorate, fuels, additives, and binders. Ignition systemsthat elevate the temperature of the solid rocket propellant to the pointof combustion are used to ignite the solid rocket fuel.

After ignition of a solid rocket motor, the reaction generally cannot beinterrupted until the fuel is completely consumed, and solid rocketpropellant burns according to the shape of the propellant grain thepropellant burn rate and its operating pressure, which is dictated bythe nozzle throat size. Thus, the burn rate of the fuel proceedsaccording to a set of predefined parameters that generally cannot bechanged during launch and/or flight.

Some solid propellants can be electrically controlled propellants thatare ignitable and extinguishable under a variety of conditions,including under high pressures within a rocket motor combustion chamber.Such electrically operated propellants can be selectively ignited andextinguished over a broad range of conditions, which facilitates theselective generation of thrust for a variety of applications, forexample, to control to a vehicle without consuming the entirety of thepropellant at one time.

SUMMARY

According to embodiments of the present invention, an electricallyoperated propellant includes an electrolyte source. The electrolytesource is an ionic liquid, a polyelectrolyte, or a combination thereof.The electrically operated propellant also includes a polymeric binder.The electrically operated propellant is substantially waterless with awater content of less than 10 wt. % water based on total weight of theelectrically operated propellant.

According to other embodiments of the present invention, an electricallyoperated propellant includes an electrolyte source. The electrolytesource is a polymer with a plurality of electrolyte groups. Theelectrically operated propellant further includes a polymeric binder.The electrically operated propellant is substantially waterless with awater content of less than 10 wt. % water based on total weight of theelectrically operated propellant.

Yet, according to other embodiments of the present invention, a methodof making an electrically operated propellant includes combining anelectrolyte source and a polymeric binder to form a propellantcomposition. The electrolyte source is an ionic liquid, apolyelectrolyte, or a combination thereof. The method further includesforming the propellant composition into a solid propellantconfiguration. The electrically operated propellant is substantiallywaterless with a water content of less than 10 wt. % water based ontotal weight of the electrically operated propellant.

Additional features and advantages are realized through the techniquesof the present invention. Other embodiments and aspects of the inventionare described in detail herein and are considered a part of the claimedinvention. For a better understanding of the invention with theadvantages and the features, refer to the description and to thedrawings.

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS

For a more complete understanding of this disclosure, reference is nowmade to the following brief description, taken in connection with theaccompanying drawings and detailed description, wherein like referencenumerals represent like parts:

FIG. 1 is a cross-sectional view of a gas generation assembly includingan electrically operated propellant; and

FIG. 2 is a flow diagram showing a method of making an electricallyoperated propellant.

DETAILED DESCRIPTION

Electrically operated propellants can be controlled (ignited,extinguished, and throttled) using an electrical signal provided by oneor more configured electrodes. For example, applying a voltage acrossthe electrodes ignites the propellant, and conversely, the interruptingthe voltage extinguishes the propellant. In a rocket motor, it may bedesirable to throttle or interrupt the burn of the electrically operatedpropellant during vehicle flight in order to control the rocket motorburn during different flight events in order to accomplish a desiredmission in a variable environment.

Generally, electrically operated solid propellants include a perchlorateoxidizer, a metal fuel, a polymeric binder, and a solvent. Water hasmost commonly been used to solubilize the polymeric binder and form anaqueous solution with the additional propellant ingredients.

One challenge of using electrically operated propellants, in asignificantly cold space propulsion application scenario, for example,is that the water used to form aqueous solutions can boil, due to thepressure drop, or freeze, due to the low temperatures, if exposeddirectly to a space environment. Even if the water in the propellant isnot directly exposed to the space environment, the included wateringredient poses an overall issue due to the significantly high and/orlow temperature and pressure exposure in space. Risks of the water inthe electrically operated propellants include potentially rendering thepropellant inoperable are therefore undesirable for space applications.

Similarly, the water in electrically operated propellants that are usedin other applications, such as in airbag inflators, presents challengesbecause including volatile components in the formulation that could belabile are problematic. This volatility makes using electricallyoperated propellants with significant quantities of water challenging,as water content verification and continuous absorption and loss ofwater despite manufacturing, storage, and use in controlled environmentspose additional water related issues.

Additionally, long term storage of an electrically operated propellantwith a water ingredient is challenging, as water may interact with othermaterials, the propellant, rocket motor, and/or flight vehicle. Further,water presents challenges with respect to with propellant relaxation outof the desired propellant shape, oxidations, as well as materialcompatibility with additional materials used in the rocket motor build.

Accordingly, one or more aspects of the present invention address theabove-described shortcomings by providing electrically operatedpropellants and methods of making and using electrically operatedpropellants, which are substantially waterless in some embodiments, andwaterless in other embodiments. In one or more aspects of the presentinvention, the electrically operated propellants include an electrolytesource, a metal fuel, a polymeric binder, and optionally, a perchlorateoxidizer, with the electrolyte source being an ionic liquid, apolyelectrolyte, or a combination thereof. In other aspects of thepresent invention, the electrically operated propellants include anelectrolyte source, a metal fuel, a polymeric binder, and optionally, aperchlorate oxidizer, with the electrolyte source being a polymer with aplurality of electrolyte groups.

Aspects of the present invention provide various advantages. Water isreduced or completely eliminated in electrically operated propellantcompositions. Further, any aqueous solvents, such as water, which arerequired for water soluble binders (e.g., casein, methyl cellulose,polyethylene oxide, polyvinyl acetate, and polyvinyl alcohol) arereplaced by a non-aqueous solvent(s), which includes one or more of anionic liquid, polyelectrolyte, or polymer with a plurality ofelectrolyte groups. The non-aqueous compositions eliminate the risk ofwater rendering the propellant inoperable when exposed directly orindirectly to a space environment in a space propulsion application(e.g., a rocket motor). Eliminating volatile water also allows theelectrically operated propellant to be used in other non-spaceapplications where water loss or absorption is undesired, for example,in airbag inflators.

The term “substantially waterless” or “non-aqueous” and variationsthereof is used in this detailed description to mean a water content ofless than 10 weight % (wt. %) water, less than 5 wt. % water, or lessthan 0.1 wt. % water. In some aspects, substantially waterless meanscompletely waterless, with 0 wt. % water present in the composition.

The term “ionic liquid” and variations thereof are used in this detaileddescription to mean a salt that melts into a liquid without decomposingor vaporizing.

The term “polyelectrolyte” and variations thereof are used in thisdetailed description to mean a polymer that includes a plurality ofelectrolyte groups (cations, anions, or a combination thereof).

The term “electrolyte source” and variations thereof are used in thisdetailed description to mean a substance that produces an electricallyconducting solution of ions when dissolved in a suitable solvent.

As described above, electrically operated propellants described hereininclude, but are not limited to, an electrolyte source, a metal fuel, apolymeric binder, and optionally a perchlorate oxidizer, with theelectrolyte source being an ionic liquid, a polyelectrolyte, a polymercomprising a plurality of electrolyte groups, or a combination thereof.The electrically operated propellants are substantially waterless andinclude a water content of less than 10 weight % (wt. %) water, lessthan 5 wt. % water, or less than 0.1 wt. % water. In some embodiments,substantially waterless electrically operated propellants are waterless,with 0 wt. % water.

Ionic liquids in the electrically operated propellants are salts thatmelt into a liquid without decomposing or vaporizing. In some aspects,ionic liquids are liquid at a temperature below 100° C. The ionicliquids are “energetic” or “nonenergetic” ionic liquids. The term“energetic” and variations thereof is intended to describe a substancewith a neutral or positive oxygen balance. Ionic liquids are salts inthe liquid state, which in some embodiments, have a melting point below25° C. Ionic liquids melt without decomposing or vaporizing. Ionicliquids are also be referred to as liquid electrolytes, ionic melts,ionic fluids, fused salts, liquid salts, and ionic glasses.

Non-limiting examples of ionic liquids for the electrically operatedpropellants include 1-(2-hydroxyethyl)-3-methylimidazolium chloride;1-butyl-3-methylimidazolium perchlorate; 1-alkyl-3-methyl imidazoliumtetrafluoroborate; 4-amino-1-butyl-1,2,4-triazolium nitrate or anycombination thereof.

In some aspects of the present invention,1-(2-hydroxyethyl)-3-methylimidazolium chloride functions as aplasticizer that improves processing. In other aspects of the presentinvention, 1-butyl-3-methylimidazolium perchlorate is included in theelectrically operated propellants to function as both the electrolytesource and an oxidizer, as it is a perchlorate-based electrolyte. Otherperchlorate-based ionic liquids can be used in the electrically operatedpropellants.

In one or more aspects of the present invention, the ionic liquid in theelectrically operated propellant is a polymerized ionic liquid.Polymerized ionic liquids include a liquid ionic species (electrolytegroup) in each repeating monomeric unit. Polymerized ionic liquidsprovide advantages in the electrically operated propellants, includingenhanced stability, improved processability, flexibility, anddurability, among others. In other aspects of the present invention, theionic liquid includes a metal (a metal ionic liquid).

Polyelectrolytes are polymers that include a plurality of electrolytegroups (cations, anions, or a combination thereof). Non-limitingexamples of polyelectrolytes include polycations, polyanions,polyampholytes, or a combination thereof.

The amount of the electrolyte source present in the electricallyoperated propellant varies depending on the type of electrolyte sourceand end propellant/application. According to some aspects of the presentinvention, the electrically operated propellant includes the electrolytesource in an amount of about 20 to about 90 percent of the total weightof the electrically operated propellant. According to other aspects ofthe present invention, the electrically operated propellant includes theelectrolyte source in an amount of about 30 to about 80 percent of thetotal weight of the electrically operated propellant.

In some aspects of the present invention, the electrolyte source canalso function as the oxidizer, and the electrically operated propellantsdo not include additional oxidizers. Yet, in other aspects of thepresent invention, the electrically operated propellants include aseparate perchlorate oxidizer, in addition to the electrolyte source.

Non-limiting examples of perchlorate oxidizers include perchlorateoxidizers such as aluminum perchlorate, ammonium perchlorate, bariumperchlorate, calcium perchlorate, lithium perchlorate, magnesiumperchlorate, perchlorate acid, strontium perchlorate, sodiumperchlorate, or any combination thereof.

The amount of the perchlorate oxidizer present in the electricallyoperated propellant varies depending on the type of oxidizer and endpropellant/application. According to some aspects of the presentinvention, the electrically operated propellant includes a perchlorateoxidizer in an amount of about 30 to about 90 percent of the totalweight of the electrically operated propellant. According to otheraspects of the present invention, the electrically operated propellantincludes a perchlorate oxidizer in an amount of about 45 to about 75percent of the total weight of the electrically operated propellant.

The electrically operated propellant further includes, optionally, ametal fuel. The metal fuel assists propellant operation in several ways,including but not limited to, facilitating the application of anelectrical signal or by increasing the density of the propellant.Non-limiting examples of the metal fuel include tungsten, magnesium,copper oxide, copper, titanium, aluminum, or any combination thereof.

The amount of the metal fuel present in the electrically operatedpropellant varies depending on the type of fuel and endpropellant/application. According to some aspects of the presentinvention, the electrically operated propellant includes a metal fuel inan amount of about 0 to about 40 percent of the total weight of theelectrically operated propellant. When included, the electricallyoperated propellant includes less than 40 percent weight of the totalweight of the electrically operated propellant. According to otheraspects of the present invention, the electrically operated propellantincludes a metal fuel in an amount of about 0 to about 30 percent of thetotal weight of the electrically operated propellant.

The electrically operated propellant further includes a polymericbinder. The polymeric binder is a water-soluble binder, a waterinsoluble polymeric binder, or a combination thereof.

Non-limiting examples of water-soluble polymeric binders include casein,methyl cellulose, polyethylene oxide, polyvinyl acetate, polyvinylalcohol, or any combination thereof.

Non-limiting examples of water insoluble polymeric binders includepolymer electrolytes, water insoluble copolymers, or a combinationthereof.

A polymer electrolyte is an electrically conducting solution of a saltin a polymer. Solid or gel polymer electrolytes are blends containing anelectrically conductive polymer, a metal salt, a finely dividedinorganic filler material, and a finely divided ion conductor. Thepolymer electrolyte is a solid polymer electrolyte, a gel polymerelectrolyte, a dry solid polymer electrolyte, or a composite polymerelectrolyte.

The water insoluble polymeric binder is also a copolymer, such as acopolymer binder system. A non-limiting example of a water insolublecopolymer is polyurethane.

The amount of the polymeric binder present in the electrically operatedpropellant varies depending on the type of water insoluble polymericbinder and end propellant/application. According to some aspects of thepresent invention, the electrically operated propellant includes apolymeric binder in an amount of about 10 to about 50 percent of thetotal weight of the electrically operated propellant. According to otheraspects of the present invention, the electrically operated propellantincludes a polymeric binder in an amount of about 15 to about 30 percentof the total weight of the electrically operated propellant.

The electrically operated propellant can be used in a variety ofapplications, such as a gas generation system of a rocket motor. Otherapplications for the electrically operated propellant include, but arenot limited to, other forms of gas generations systems used in place oftraditional solid or liquid rocket motor solutions, such as orbitmaintenance systems, divert/attitude control systems, and ignitionsystems, in additional to as a replacement for traditional and smart airbag inflator systems, as well as ejection systems.

The polymeric binder cooperates with the electrolyte source, metal fuel,and optional perchlorate oxidizer to combine these components into asolid fuel propellant shapeable into any configuration such as thecylindrical configurations provided in FIG. 1, which is described infurther detail below. The electrically operated propellant has a storagemodulus sufficiently high to allow for the maintenance of the shape thepropellant is molded into at manufacture. For instance, the electricallyoperated propellant has a storage modulus of 300 psi or greater atambient temperature that accordingly allows the propellant in theconfigurations shown in FIG. 1 or other configurations to maintain itsshape through dynamic conditions including, but not limited to,pressurization, launch and flight. The propellant with a consistentshape accordingly maintains a predictable performance profile as theshape and surface area of the propellant are relatively static duringoperation. The electrically operated propellant is thereby formable(e.g., can be cast or molded) into any number of grain configurationsand reliably perform with a desired performance profile (thrust dictatedat least in part by the grain surface area) even when subject to dynamicconditions.

FIG. 1 depicts a cross-sectional view of a gas generation assemblyincluding an electrically operated propellant according to aspects ofthe present invention. It is to be noted that the gas generation systemwith electrically operated propellant shown in FIG. 1 is but oneexample, and the electrically operated propellant can be used in otherconfigurations, applications, and gas generation systems.

The gas generation system 100 is shown as part of an overall assembly,such as a rocket motor 102. In one example, the gas generation system100 includes the rocket motor 102. The gas generation system 100includes the electrically operated propellant 108, configured to providethrust through a rocket nozzle 112.

The gas generation system 100 includes a combustion chamber of 104having the electrically operated propellant 108 positioned therein. Twoor more electrodes 110 extend into the electrically operated propellant108 within the combustion chamber 104. The electrically operatedpropellant 108 fills a portion of combustion chamber 104 and has apredetermined grain shape. In another example, the electrically operatedpropellant 108 fills substantially the entirety of the combustionchamber 104. That is to say, the electrically operated propellant 108extends from the position shown in FIG. 1 toward a position in closeproximity to the nozzle 112. Accordingly, the two or more electrodes 110similarly extend through the electrically operated propellant 108 towardthe nozzle 112.

The electrically operated propellant 108 includes a formulation thatallows for the igniting and extinguishing of the propellant in a varietyof conditions according to the application (and interruption of theapplication) of electricity through the electrodes 110. For instance,the electrically operated propellant 108 is configured to ignite withthe application of voltage across the electrodes 110. Conversely, theelectrically operated propellant 108 is extinguished with theinterruption of the voltage at a range of pressures (e.g., from 0 psi to2,000 psi). For instance, where the combustion chamber 104 is part ofthe rocket motor 102, and the motor is in the process of generatingthrust, the pressure within the combustion chamber 104 is greater than200 psi, for instance from 200 to 2,000 psi. In this condition, it maybe desirable to interrupt the burn of the electrically operatedpropellant, for example, in order to provide changing levels of thrustfor a mission with variable requirements. In such a circumstance thevoltage applied across the electrodes 110 is interrupted. Despite thepressurized environment of the combustion chamber 104, subjecting theelectrically operated propellant 108 to a pressure greater than 200 psi,for instance pressures approaching 2,000 psi, the interruption ofvoltage to the electrodes 110 allows the electrically operatedpropellant 108 to extinguish. With the electrically operated propellant108 extinguished, the generation of thrust is halted and the propellantis preserved for future use. The gas generation systems 100 isconfigured for ignition and extinguishing during operation. Importantly,even with ambient or high pressures within the combustion chamber 104,such as atmospheric pressure, pressures greater than 200 psi, 500 psi,1,000 psi, 1,500 psi and up to 2,000 psi, the electrically operatedpropellant 108 is extinguished with the interruption of electricity(e.g., voltage or current) applied across the electrodes 110.

FIG. 2 is a flow diagram showing a method 200 of making an electricallyoperated propellant according to some aspects of the present invention.As shown in box 202, an electrolyte source, an optional metal fuel, anda polymeric binder are combined to form a propellant composition. Themetal fuel is optional, and in some embodiments, the metal fuel is notincluded in the propellant composition. As shown in box 204, anyadditional formulation components are added into the propellantcomposition. As shown in box 206, the propellant composition is machineprocessed for a specified time, under specified conditions (temperature,pressure, machine settings, etc.), depending on the particularpropellant and configuration. As shown in box 208, the machine processedcomposition is formed into a solid propellant configuration. Thepropellant composition is moldable, extrudable, castable, pressable, ora combination thereof, depending on the application. As shown in box210, the solid propellant configuration is set for a specified amount oftime in a controlled environment (temperature, pressure, humidity,etc.), depending on the particular propellant and application.

Various embodiments of the present invention are described herein withreference to the related drawings. Alternative embodiments can bedevised without departing from the scope of this invention. Althoughvarious connections and positional relationships (e.g., over, below,adjacent, etc.) are set forth between elements in the followingdescription and in the drawings, persons skilled in the art willrecognize that many of the positional relationships described herein areorientation-independent when the described functionality is maintainedeven though the orientation is changed. These connections and/orpositional relationships, unless specified otherwise, can be direct orindirect, and the present invention is not intended to be limiting inthis respect. Accordingly, a coupling of entities can refer to either adirect or an indirect coupling, and a positional relationship betweenentities can be a direct or indirect positional relationship. As anexample of an indirect positional relationship, references in thepresent description to forming layer “A” over layer “B” includesituations in which one or more intermediate layers (e.g., layer “C”) isbetween layer “A” and layer “B” as long as the relevant characteristicsand functionalities of layer “A” and layer “B” are not substantiallychanged by the intermediate layer(s).

The following definitions and abbreviations are to be used for theinterpretation of the claims and the specification. As used herein, theterms “comprises,” “comprising,” “includes,” “including,” “has,”“having,” “contains” or “containing,” or any other variation thereof,are intended to cover a non-exclusive inclusion. For example, acomposition, a mixture, process, method, article, or apparatus thatcomprises a list of elements is not necessarily limited to only thoseelements but can include other elements not expressly listed or inherentto such composition, mixture, process, method, article, or apparatus.

Additionally, the term “exemplary” is used herein to mean “serving as anexample, instance or illustration.” Any embodiment or design describedherein as “exemplary” is not necessarily to be construed as preferred oradvantageous over other embodiments or designs. The terms “at least one”and “one or more” are understood to include any integer number greaterthan or equal to one, i.e. one, two, three, four, etc. The terms “aplurality” are understood to include any integer number greater than orequal to two, i.e. two, three, four, five, etc. The term “connection”can include an indirect “connection” and a direct “connection.”

References in the specification to “one embodiment,” “an embodiment,”“an example embodiment,” etc., indicate that the embodiment describedcan include a particular feature, structure, or characteristic, butevery embodiment may or may not include the particular feature,structure, or characteristic. Moreover, such phrases are not necessarilyreferring to the same embodiment. Further, when a particular feature,structure, or characteristic is described in connection with anembodiment, it is submitted that it is within the knowledge of oneskilled in the art to affect such feature, structure, or characteristicin connection with other embodiments whether or not explicitlydescribed.

For purposes of the description hereinafter, the terms “upper,” “lower,”“right,” “left,” “vertical,” “horizontal,” “top,” “bottom,” andderivatives thereof shall relate to the described structures andmethods, as oriented in the drawing figures. The terms “overlying,”“atop,” “on top,” “positioned on” or “positioned atop” mean that a firstelement, such as a first structure, is present on a second element, suchas a second structure, wherein intervening elements such as an interfacestructure can be present between the first element and the secondelement. The term “direct contact” means that a first element, such as afirst structure, and a second element, such as a second structure, areconnected without any intermediary conducting, insulating orsemiconductor layers at the interface of the two elements.

The terms “about,” “substantially,” “approximately,” and variationsthereof, are intended to include the degree of error associated withmeasurement of the particular quantity based upon the equipmentavailable at the time of filing the application. For example, “about”can include a range of ±8% or 5%, or 2% of a given value.

The flowchart and block diagrams in the Figures illustrate possibleimplementations of fabrication and/or operation methods according tovarious embodiments of the present invention. Variousfunctions/operations of the method are represented in the flow diagramby blocks. In some alternative implementations, the functions noted inthe blocks can occur out of the order noted in the Figures. For example,two blocks shown in succession can, in fact, be executed substantiallyconcurrently, or the blocks can sometimes be executed in the reverseorder, depending upon the functionality involved.

The corresponding structures, materials, acts, and equivalents of allmeans or step plus function elements in the claims below are intended toinclude any structure, material, or act for performing the function incombination with other claimed elements as specifically claimed. Thedescription of the present invention has been presented for purposes ofillustration and description, but is not intended to be exhaustive orlimited to the invention in the form disclosed. Many modifications andvariations will be apparent to those of ordinary skill in the artwithout departing from the scope and spirit of the invention. Theembodiments were chosen and described in order to best explain theprinciples of the invention and the practical application, and to enableothers of ordinary skill in the art to understand the invention forvarious embodiments with various modifications as are suited to theparticular use contemplated.

While the preferred embodiments to the invention have been described, itwill be understood that those skilled in the art, both now and in thefuture, may make various improvements and enhancements which fall withinthe scope of the claims which follow. These claims should be construedto maintain the proper protection for the invention first described.

What is claimed is:
 1. An electrically operated propellant comprising:an electrolyte source, the electrolyte source being an ionic liquid, apolyelectrolyte, or a combination thereof; and a polymeric binder;wherein the electrically operated propellant is substantially waterlesswith a water content of less than 10 wt. % water based on total weightof the electrically operated propellant.
 2. The electrically operatedpropellant of claim 1, wherein the ionic liquid is a salt that meltsinto a liquid without decomposing or vaporizing.
 3. The electricallyoperated propellant of claim 1, wherein the electrically operatedpropellant is waterless with a water content of 0 wt. % water.
 4. Theelectrically operated propellant of claim 1, further comprising aperchlorate oxidizer.
 5. The electrically operated propellant of claim1, wherein the electrolyte source is a perchlorate-based electrolytesource.
 6. The electrically operated propellant of claim 1, wherein thepolyelectrolyte is a polycation, a polyanion, a polyampholyte, or acombination thereof.
 7. The electrically operated propellant of claim 1,wherein the ionic liquid comprises a metal.
 8. The electrically operatedpropellant of claim 1, wherein the ionic liquid is1-(2-hydroxyethyl)-3-methylimidazolium chloride;1-butyl-3-methylimidazolium perchlorate; 1-alkyl-3-methyl imidazoliumtetrafluoroborate; 4-amino-1-butyl-1,2,4-triazolium nitrate or anycombination thereof.
 9. An electrically operated propellant comprising:an electrolyte source, the electrolyte source being a polymer comprisinga plurality of electrolyte groups; and a polymeric binder; wherein theelectrically operated propellant is substantially waterless with a watercontent of less than 10 wt. % water based on total weight of theelectrically operated propellant.
 10. The electrically operatedpropellant of claim 9, wherein the electrically operated propellant iswaterless with a water content of 0 wt. % water.
 11. The electricallyoperated propellant of claim 9, further comprising a metal fuel.
 12. Theelectrically operated propellant of claim 9, wherein the polymercomprising the plurality of electrolyte groups is a polymerized ionicliquid.
 13. The electrically operated propellant of claim 9, wherein thepolymer comprising the plurality of electrolyte groups is a polycation,a polyanion, a polyampholyte, or a combination thereof.
 14. Theelectrically operated propellant of claim 9, further comprising aperchlorate oxidizer.
 15. A method of making an electrically operatedpropellant, the method comprising: combining an electrolyte source and apolymeric binder to form a propellant composition, the electrolytesource being an ionic liquid, a polyelectrolyte, or a combinationthereof; and forming the propellant composition into a solid propellantconfiguration; wherein the electrically operated propellant issubstantially waterless with a water content of less than 10 wt. % waterbased on total weight of the electrically operated propellant.
 16. Themethod of claim 15, wherein the ionic liquid is a salt that melts into aliquid without decomposing or vaporizing.
 17. The method of claim 15,wherein the ionic liquid is a polymerized ionic liquid.
 18. The methodof claim 15, wherein the polyelectrolyte is a polycation, a polyanion, apolyampholyte, or a combination thereof.
 19. The method of claim 15,further comprising combining a metal fuel with the electrolyte sourceand the polymeric binder.
 20. The method of claim 15, wherein theelectrically operated propellant is waterless with a water content of 0wt. % water.